[go: up one dir, main page]

EP2930371B1 - Turbomaschine mit einem extraktionsport - Google Patents

Turbomaschine mit einem extraktionsport Download PDF

Info

Publication number
EP2930371B1
EP2930371B1 EP15160825.4A EP15160825A EP2930371B1 EP 2930371 B1 EP2930371 B1 EP 2930371B1 EP 15160825 A EP15160825 A EP 15160825A EP 2930371 B1 EP2930371 B1 EP 2930371B1
Authority
EP
European Patent Office
Prior art keywords
impeller
openings
turbomachine
shroud
impeller shroud
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP15160825.4A
Other languages
English (en)
French (fr)
Other versions
EP2930371A1 (de
Inventor
Michael Todd Barton
John Schugardt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Honeywell International Inc
Original Assignee
Honeywell International Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Honeywell International Inc filed Critical Honeywell International Inc
Publication of EP2930371A1 publication Critical patent/EP2930371A1/de
Application granted granted Critical
Publication of EP2930371B1 publication Critical patent/EP2930371B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface

Definitions

  • the present invention relates generally to turbomachines and, more particularly, to auxiliary power units and gas turbine engines.
  • Turbomachines include gas turbine engines such as auxiliary power units, propulsive gas turbine engines deployed onboard aircraft and other vehicles, turboshaft engines utilized for industrial power generation, and non-gas turbine engines, such as turbochargers.
  • a turbomachine includes a compressor section, a combustion section, and a turbine section.
  • the compressor section draws ambient air into the inlet of the turbomachine, compresses the inlet air with one or more compressors, and supplies the compressed inlet air to the combustion section.
  • the combustion section also receives fuel via a fuel injection assembly, mixes the fuel with the compressed air, ignites the mixture, and supplies the high energy hot combustion gases to the turbine section.
  • the turbine section drives one or more turbines, including a shaft that may be used to drive the compressor and other components.
  • the flowpath is defined by air moving through the stages in the turbomachine, inclusive of the inlet air, compressed inlet air and hot combustion gases.
  • Turbomachines often employ centrifugal compressors as a means to compress air prior to delivery into the engine's combustion chamber.
  • the rotating element of the centrifugal compressor commonly referred to as an impeller, is typically surrounded by a generally conical or bell-shaped shroud, which helps guide air in the flowpath from the forward section (commonly referred to as the "inducer” section) to the aft section of the impeller (commonly referred to as the "exducer” section).
  • Some conventional impeller designs commonly referred to as ported shroud impellers, boost performance by extracting air from the flowpath through various methods. Air flow may be extracted in either of two directions, depending upon the operational conditions of the impeller. Conventional ported shroud impeller designs then either reintroduce the extracted air into the flowpath (typically at the impeller inlet) or dump the extracted air overboard (with an associated penalty to the engine cycle).
  • the conventional ported shroud impeller when the impeller is operating near the choke side of its operating characteristic, the conventional ported shroud impeller "inflows" or reintroduces extracted air into the flow path (that is, draws air into the impeller through at least one opening) to increase the choke side range of the impeller operating characteristic; and, when the impeller is operating near the stall side of its operating characteristic, the conventional impeller shroud outflows (that is, bleeds or extracts air from the impeller through at least one opening) to increase the stall side range of the impeller operating characteristic. While conventional ported shroud impellers of the type described above can increase impeller performance within limits, further improvements in efficiency are desirable.
  • WO2013/111780 describes a turbomachine with a conventional shroud impeller.
  • the present invention provides a turbomachine as defined in claim 1. Further embodiments are defined in the dependent claims.
  • Coupled means that one element/node/feature is directly or indirectly joined to (or directly or indirectly communicates with) another element/node/feature, and not necessarily mechanically.
  • drawings may depict one exemplary arrangement of elements, additional intervening elements, devices, features, or components may be present in an embodiment of the depicted subject matter.
  • FIG. 1 is a simplified schematic illustration of a turbomachine 12 including a compressor module 16 , a combustor module 18 , and a turbine module 20 .
  • the compressor module 16 , combustor module 18 , and turbine module 20 are in air flow communication.
  • Compressor module 16 and turbine module 20 are coupled by a shaft 22 .
  • Shaft 22 rotates about an axis of symmetry, which is the centerline of the shaft 22 .
  • the shaft 22 forms the longitudinal axis of the turbomachine, also referred to as the engine centerline.
  • air flows from the inlet of the turbomachine, as inlet air 15 , through the compressor module 16 , where it is compressed.
  • Compressed air 80 is then provided to combustor module 18 where it is mixed with fuel 17 provided by fuel nozzles (not shown). The fuel/air mixture is then ignited within the combustor module 18 to produce hot combustion gases 19 that drive turbine module 20 .
  • the flowpath is defined by air flow moving through the stages in the turbomachine, inclusive of the inlet air 15 , compressed air 80 and hot combustion gases 19 .
  • centrifugal compressors are often utilized within the compressor module of a turbomachine to compress air flow prior to delivery into the engine's combustion chamber. It is to be understood that in the exemplary embodiments herein, only one compressor and one turbine are shown for ease of illustration, but multiple compressors and turbines may be present in various stages of a turbomachine.
  • FIG. 2 is a side cross-sectional schematic illustration of a portion of an exemplary compressor module 16 of the type used in turbomachine 12 .
  • Compressor module 16 includes an impeller 202 .
  • the impeller 202 includes an impeller inlet 204 (defined in part by an inlet edge of the impeller shroud 222 ), an impeller exit 206 (defined in part by an outlet edge of the impeller shroud), an impeller hub 208 , and a rotating impeller body 210 extending therebetween.
  • inlet air 15 flows from impeller inlet 204 to impeller exit 206 .
  • the impeller 202 also includes a non-rotating conventional impeller shroud 212 that extends around, or surrounds, a portion of the impeller body 210 , as hereinafter described.
  • the impeller body 210 and impeller shroud 212 extend radially outward from the impeller inlet 204 to the impeller exit 206 .
  • Impeller hub 208 is coupled circumferentially to a rotor shaft (not shown).
  • At least one opening 214 may be disposed in the impeller shroud 212 between the impeller inlet 204 and impeller exit 206 ; the opening 214 providing fluid communication between the impeller portion of the flowpath and the plenum 220 .
  • the opening 214 is circumferentially aligned at a radial distance 216 , drawn perpendicularly from the engine centerline 218 .
  • the opening 214 in the impeller shroud 212 is located between the impeller inlet 204 and the impeller exit 206 , and provides fluid communication between the plenum 220 and the impeller flowpath.
  • the shroud 212 may be about .075 inches (1.9 cm) thick to about 0.400 inches (1.02 cm) thick, but other thicknesses for the impeller shroud 212 may be used depending on operating conditions and performance requirements of the turbine engines in addition to geometry and manufacturing constraints, as known to one skilled in the art.
  • Opening 214 is substantially circular in the exemplary embodiments described in FIGS 3 thru 6 ; having a diameter of about 0.010 inch (0.25 mm) to about 0.300 inch; inch (7.62 mm); however in some embodiments, opening 214 may have an oval shape, may be slot-shaped defined by a width of about 0.1 inch (2.54 mm) to about 0.6 inch (15.24 mm), or any other shape that permits fluid communication with the dead-headed plenum. According to the invention, openings have the same dimensions, and/or be equally spaced, but this is not a requirement
  • Plenum 220 is otherwise a closed cavity, i.e., there are no other openings into plenum 220 to support any other active or passive ingress or egress of air; therefore, plenum 220 is herein referred to as a dead-headed plenum.
  • plenum 220 does not communicate with an outside environment, thus reducing the likelihood of the introduction of dirt or other foreign debris into the impeller flowpath.
  • Plenum 220 may take the form of a variety of shapes and volumes, while continuing to be a dead-headed plenum as described herein, and while continuing to be in fluid communication with the impeller flowpath.
  • the embodiments described herein provide a gain in compressor efficiency without extracting air (conventionally referred to as bleed flow extraction) from the cavity, and there is no loss in surge margin utilizing this technique.
  • the gain is recognized over a variety of cavity shapes and cavity volumes.
  • FIG. 3 is the cross-sectional schematic illustration of FIG. 2 showing exemplary locations for openings in the impeller shroud 212.
  • FIG. 3 depicts opening 214 circumferentially aligned at radial distance 216 , opening 302 circumferentially aligned at radial distance 306 , and opening 304 circumferentially aligned at radial distance 308 .
  • Plenum 220 is depicted as a dead-headed cavity except for the openings through the impeller shroud 212 .
  • Radial distance is measured perpendicular to the longitudinal axis of the turbomachine, or the engine centerline 218 .
  • the openings in the impeller shroud can be located anywhere along the shroud between impeller inlet 204 and impeller exit 206 .
  • FIG. 4 is an enlarged view of FIG. 3 showing exemplary locations for openings.
  • FIG 4 depicts impeller shroud 212 , impeller inlet 204 , impeller exit 206 , and plenum 220 .
  • opening 402 is measured from the longitudinal axis of the turbomachine, or the engine centerline 218 .
  • the centerline axis of an opening is not perpendicular to the engine centerline.
  • opening 406 is depicted with a centerline axis having an angle 414 from the perpendicular line representing the radial distance 408.
  • FIG. 5 is a three-dimensional rendering of an impeller shroud 500 according to an embodiment of the invention.
  • a plurality of openings 518 are depicted as having substantially the same dimensions, being substantially medially located, and being substantially circumferentially aligned on the surface of the impeller shroud 502 .
  • the openings are located at a predetermined radial distance (e.g., radial distance 508 ) from the longitudinal axis or engine centerline 512 .
  • radial distance 508 is depicted at angle 514 from engine centerline 512 .
  • the angle 514 is ninety degrees and radial distance lines are perpendicular to the longitudinal axis, but in other embodiments the angle may vary.
  • the openings are disposed within the region defined by the inlet edge of the impeller shroud 504 and a substantially medial line 520 circumferentially around impeller shroud 502 referred to herein as the "knee".
  • the knee may be arrived at by incrementally increasing the radial distance described hereinabove, concurrent with moving along the longitudinal axis from the inlet edge of the impeller shroud (co-aligned with the impeller inlet 204 ) toward the impeller exit 206 .
  • the knee is substantially midpoint on the impeller shroud and may represent a point of inflection on the impeller shroud surface.
  • the radial distance used for the placement of the openings varies in different embodiments of the turbomachine, since the location of the openings for ideal performance may vary from one compressor design to the next. In some embodiments which do not form part of the claimed invention, the radial distance varies from one opening to another, resulting in openings that are not circumferentially aligned, as is depicted in FIG. 6 .
  • FIG. 6 is three-dimensional rendering of an impeller shroud 600 according to a further exemplary embodiment which does not form part of the claimed invention.
  • a plurality of openings 601 are depicted on the surface of the impeller shroud 614 . As described hereinabove, the openings are located at a radial distance from the engine centerline 602 .
  • openings 601 are depicted at different radial distances from the longitudinal axis or engine centerline 602 , but still located between the inlet edge of the impeller shroud 612 and the edge of the impeller exit 622 .
  • opening 604 is located at radial distance 606
  • opening 620 is located at radial distance 618 ; opening 608 is also shown between the inlet edge of the impeller shroud and the edge of the impeller exit 622 .
  • the other openings in the impeller shroud may be generated by rotating the impeller shroud to define an opening pattern.
  • the other openings may have substantially the same radial distance, and substantially the same centerline axis angle as the first opening.
  • the centerline axis of each of openings in the impeller shroud may be determined independently using the multiple rotation angles. In some embodiments the distance between adjacent pairs of openings is substantially equal, however this is not required.
  • embodiments of a turbomachine and, specifically, an auxiliary power unit including an impeller shroud with openings communicating with a dead-headed plenum improving efficiency can be implemented in a relatively low cost, low part count and straightforward manner and provides reliable, passive operation.
  • embodiments of the above-described impeller shroud system can also be installed as a retrofit into existing turbomachine, such as service-deployed auxiliary power unit. While primarily described in the context of a particular type of turbomachine, namely, an auxiliary power unit, it is emphasized that embodiments of the impeller shroud system can be utilized in conjunction with other types of gas turbine engines and turbomachines including turbochargers.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (5)

  1. Turbomaschine (12), die eine Längsachse und einen Strömungspfad aufweist, die einen Verdichter umfasst, wobei der Verdichter Folgendes umfasst:
    ein Laufrad (202), das umfänglich um die Längsachse (218) angeordnet ist;
    ein Laufraddeckband (502), das eine Oberfläche umfasst, die eine Einlasskante und eine Auslasskante aufweist, wobei das Laufraddeckband (502) an einen Abschnitt des Laufrads gekoppelt ist und sich darum erstreckt;
    wobei die Turbomaschine (12) ferner Folgendes umfasst:
    eine Vielzahl von Öffnungen, die durch das Laufraddeckband (502) gebildet ist, die innerhalb eines Bereichs angeordnet ist, der von der Einlasskante (504) des Laufraddeckbands und einer im Wesentlichen medialen Linie (520) umfänglich um das Laufraddeckband (502) definiert ist, wobei die mediale Linie (520) einen Mittelpunkt auf dem Deckband definiert;
    wobei jede Öffnung der Vielzahl von Öffnungen Fluidkommunikation zwischen dem Strömungspfad und einem Totraumplenum (220) bereitstellt, wobei keine anderen Öffnungen in dem Totraumplenum vorhanden sind;
    wobei die Öffnungen jeweils eine jeweilige Mittenlinienachse aufweisen und sich auf dem Laufraddeckband (502) in einem jeweiligen radialen Abstand (508) befinden, der senkrecht von der Längsachse ausgehend gemessen ist, und
    wobei für jede Öffnung ihre Mittenlinienachse einen Winkel in Bezug zu dem radialen Abstandsmaß bildet, dadurch gekennzeichnet, dass die Mittenlinienachse jeder Öffnung nicht zu der Längsachse senkrecht ist, und dadurch, dass jede der Vielzahl von Öffnungen dieselben Abmessungen aufweist, medial liegt und umfänglich an der Oberfläche des Laufraddeckbands ausgerichtet ist.
  2. Turbomaschine nach Anspruch 1, wobei die im Wesentlichen mediale Linie (520) umfänglich um die Oberfläche des Laufraddeckbands (502) einen Krümmer definiert.
  3. Turbomaschine nach Anspruch 2, wobei jede der Vielzahl von Öffnungen in demselben vorbestimmten ersten radialen Abstand (508) von der Längsachse liegt.
  4. Turbomaschine nach Anspruch 1, wobei für die Vielzahl von Öffnungen ein Abstand zwischen angrenzenden Paaren von Öffnungen im Wesentlichen gleich ist.
  5. Turbomaschine nach Anspruch 1, wobei für die Vielzahl von Öffnungen ein Abstand zwischen angrenzenden Paaren von Öffnungen im Wesentlichen unterschiedlich ist.
EP15160825.4A 2014-04-09 2015-03-25 Turbomaschine mit einem extraktionsport Active EP2930371B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/248,579 US9650916B2 (en) 2014-04-09 2014-04-09 Turbomachine cooling systems

Publications (2)

Publication Number Publication Date
EP2930371A1 EP2930371A1 (de) 2015-10-14
EP2930371B1 true EP2930371B1 (de) 2023-05-03

Family

ID=52784947

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15160825.4A Active EP2930371B1 (de) 2014-04-09 2015-03-25 Turbomaschine mit einem extraktionsport

Country Status (2)

Country Link
US (1) US9650916B2 (de)
EP (1) EP2930371B1 (de)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3008750B1 (fr) * 2013-07-18 2015-07-17 Snecma Couvercle de compresseur centrifuge de turbomachine apte a etre fixe par l'aval pres de son bord amont, turbomachine comportant ce couvercle.
US10359051B2 (en) * 2016-01-26 2019-07-23 Honeywell International Inc. Impeller shroud supports having mid-impeller bleed flow passages and gas turbine engines including the same
US10208628B2 (en) * 2016-03-30 2019-02-19 Honeywell International Inc. Turbine engine designs for improved fine particle separation efficiency
US10830144B2 (en) 2016-09-08 2020-11-10 Rolls-Royce North American Technologies Inc. Gas turbine engine compressor impeller cooling air sinks
US20180135525A1 (en) * 2016-11-14 2018-05-17 Pratt & Whitney Canada Corp. Gas turbine engine tangential orifice bleed configuration
US20180135516A1 (en) 2016-11-16 2018-05-17 Honeywell International Inc. Scavenge methodologies for turbine engine particle separation concepts
US11125158B2 (en) 2018-09-17 2021-09-21 Honeywell International Inc. Ported shroud system for turboprop inlets
US11199195B2 (en) * 2019-10-18 2021-12-14 Pratt & Whitney Canada Corp. Shroud with continuous slot and angled bridges
US11525393B2 (en) 2020-03-19 2022-12-13 Rolls-Royce Corporation Turbine engine with centrifugal compressor having impeller backplate offtake
US11773773B1 (en) 2022-07-26 2023-10-03 Rolls-Royce North American Technologies Inc. Gas turbine engine centrifugal compressor with impeller load and cooling control

Family Cites Families (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB705387A (en) 1951-02-15 1954-03-10 Power Jets Res & Dev Ltd Improvements relating to radial-flow turbine or centrifugal compressors
US2970750A (en) * 1956-02-06 1961-02-07 Judson S Swearingen Centrifugal gas compression
ZA791291B (en) 1978-03-28 1980-03-26 Howden James & Co Ltd Fans or the like
US4248566A (en) 1978-10-06 1981-02-03 General Motors Corporation Dual function compressor bleed
US5253472A (en) 1990-02-28 1993-10-19 Dev Sudarshan P Small gas turbine having enhanced fuel economy
US5246335A (en) 1991-05-01 1993-09-21 Ishikawajima-Harimas Jukogyo Kabushiki Kaisha Compressor casing for turbocharger and assembly thereof
US5619850A (en) 1995-05-09 1997-04-15 Alliedsignal Inc. Gas turbine engine with bleed air buffer seal
JPH09112268A (ja) * 1995-10-19 1997-04-28 Hitachi Constr Mach Co Ltd エンジン冷却装置及び建設機械
JP3494118B2 (ja) 2000-04-07 2004-02-03 石川島播磨重工業株式会社 遠心圧縮機の作動域拡大方法及び装置
WO2005068842A1 (en) 2003-12-24 2005-07-28 Honeywell International, Inc. Recirculation port
US7775759B2 (en) 2003-12-24 2010-08-17 Honeywell International Inc. Centrifugal compressor with surge control, and associated method
US7147426B2 (en) 2004-05-07 2006-12-12 Pratt & Whitney Canada Corp. Shockwave-induced boundary layer bleed
US7407364B2 (en) 2005-03-01 2008-08-05 Honeywell International, Inc. Turbocharger compressor having ported second-stage shroud, and associated method
JP2009156122A (ja) 2007-12-26 2009-07-16 Mitsubishi Heavy Ind Ltd 遠心圧縮機用インペラ
US7946801B2 (en) * 2007-12-27 2011-05-24 General Electric Company Multi-source gas turbine cooling
US8061974B2 (en) 2008-09-11 2011-11-22 Honeywell International Inc. Compressor with variable-geometry ported shroud
US8092145B2 (en) 2008-10-28 2012-01-10 Pratt & Whitney Canada Corp. Particle separator and separating method for gas turbine engine
US8210794B2 (en) 2008-10-30 2012-07-03 Honeywell International Inc. Axial-centrifugal compressor with ported shroud
GB2467964B (en) 2009-02-24 2015-03-25 Dyson Technology Ltd Shroud-Diffuser assembly
US8221070B2 (en) 2009-03-25 2012-07-17 Woodward, Inc. Centrifugal impeller with controlled force balance
IT1394295B1 (it) 2009-05-08 2012-06-06 Nuovo Pignone Spa Girante centrifuga del tipo chiuso per turbomacchine, componente per tale girante, turbomacchina provvista di tale girante e metodo di realizzazione di tale girante
US8490408B2 (en) 2009-07-24 2013-07-23 Pratt & Whitney Canada Copr. Continuous slot in shroud
FR2964725B1 (fr) 2010-09-14 2012-10-12 Snecma Carenage aerodynamique pour fond de chambre de combustion
JP5895343B2 (ja) 2011-01-24 2016-03-30 株式会社Ihi 遠心圧縮機及び遠心圧縮機の製造方法
US20130051974A1 (en) * 2011-08-25 2013-02-28 Honeywell International Inc. Gas turbine engines and methods for cooling components thereof with mid-impeller bleed cooling air
JP5853721B2 (ja) 2012-01-23 2016-02-09 株式会社Ihi 遠心圧縮機

Also Published As

Publication number Publication date
US9650916B2 (en) 2017-05-16
EP2930371A1 (de) 2015-10-14
US20150292355A1 (en) 2015-10-15

Similar Documents

Publication Publication Date Title
EP2930371B1 (de) Turbomaschine mit einem extraktionsport
US10822957B2 (en) Fillet optimization for turbine airfoil
US10436038B2 (en) Turbine engine with an airfoil having a tip shelf outlet
EP3199822B1 (de) Laufradabdeckungsträger mit ablasskanälen in der impellermitte
EP2778427B1 (de) Selbstrückführendes Kompressorentlüftungssystem
US20170306764A1 (en) Airfoil for a turbine engine
US10267161B2 (en) Gas turbine engine with fillet film holes
US10598191B2 (en) Vane for turbomachinery, such as an aircraft turbojet or turbofan engine or an aircraft turboprop engine
US10526900B2 (en) Shrouded turbine blade
US11208901B2 (en) Trailing edge cooling for a turbine blade
US20170234141A1 (en) Airfoil having crossover holes
JP2007536459A (ja) 遷音速ガスタービンの衝撃波誘起境界層の抽気
EP2725233A1 (de) Laufschaufel für einen Verdichter
US11473435B2 (en) Turbine vane comprising a passive system for reducing vortex phenomena in an air flow flowing over said vane
US11274563B2 (en) Turbine rear frame for a turbine engine
US10329922B2 (en) Gas turbine engine airfoil
WO2018004766A1 (en) Airfoil and blade for a turbine engine, and corresponding method of flowing a cooling fluid
EP4144958B1 (de) Strömungmaschine für ein flugzeugtriebwerk und flugzeugtriebwerk
EP3159482B1 (de) Schaufelanordnung, zugehörige rotoranordnung und gasturbinenkraftwerk

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20150325

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: HONEYWELL INTERNATIONAL INC.

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20180508

RAP3 Party data changed (applicant data changed or rights of an application transferred)

Owner name: HONEYWELL INTERNATIONAL INC.

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20221107

RIN1 Information on inventor provided before grant (corrected)

Inventor name: SCHUGARDT, JOHN

Inventor name: BARTON, MICHAEL TODD

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1564822

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230515

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602015083381

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230421

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20230503

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1564822

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230904

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230803

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230903

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230804

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602015083381

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20240206

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240325

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20240325

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240325

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20240331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240325

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240325

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240325

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240325

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240331

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240331

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240331

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20250327

Year of fee payment: 11

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20150325

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20150325

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503